外文翻译--航空发动机状态监测系统设计研究

1、AeroengineconditionmonitoringsystemdesignstudyDesignresearchabstract:theaircraftengineconditionmonitoringsystemforacertaintypeofaircraftengineastheresearchobject,discussedtheenginestatemonitoringsystemdesignandimplementation,thispapermainlydiscussesthestatusmonitoringsystemoftheoveralldesign,systems

2、oftwareandhardwaredevelopmentandtestingandredundancydesign,andinthedesignofenginestatemonitoringsystem,introducedtheembeddedPC/104modules.Inordertomakethestatemonitoringsystemhasabetterscalabilityandadaptability,thesystemdesignedcanworkinthreeways:airborneoperationmode,dataplaybackmodeandgroundtestr

3、unmode,throughthesewayforautomaticmonitoringofenginestateparameter,forthestateoftheenginetrendanalysis,faultdiagnosis,andastoprovidescientificbasisformaintenance.Keywords:theengineconditionmonitoring;PC/104;Redundantdesign.0.TheintroductionAsthepowersourceoftheairplaneflight,aircraftengineresearchis

4、averycomplexprocess,theaircraftenginetestasthedevelopmentofthethreepillars(calculation,manufactureandtest),oneofitsimportanceisself-evident,itturnsout,mainlyconsistedofenginetest,ratherthanbycalculationandanalysis.Forthedevelopmentofanaircraftenginegroup,isflat,howwecandecidethehowdevelopedhorizonta

5、lengine.Foraircraftenginemanufacture,conditionmonitoringisanimportantexaminationmethodofengineperformance,byconditionmonitoringandtestingworkistoadjusttheengineperformanceandbreak-in,checkthemanufacturingoroverhaulquality,finallygivestheenginefactoryperformancereportpurpose,thereforetheaccurateandre

6、liabletestmethodforstatemonitoringtoensurethequalityoftheenginehasthevitalsignificance.Asweallknow,theenginevibrationandhighnoiseintheprocessofworkandthestrongjammingsignal,allparameterstothevarietyofthemonitoringsystemputsforwardhigherrequirements.Especiallywiththeimprovementofengineperformance,rea

7、l-timemonitoringoftheparametersneededforconditionmonitoringisbecomingmoreandmorepeoplecontinuetoexplorenewtestingtechnologyformanyyears,toadapttotheincreasinglydevelopmentofenginetesttechnologyrequirements.TheconditionmonitoringsystemoveralldesignTheconditionmonitoringsystemisdesignedforacertaintype

8、ofturbofanengine,theenginemonitoringsystemoftheinputsignalispartofatotalof17analog,3road16wayswitchfrequencyandquantity,including17analog,3roadfrequencyquantitythroughthesignalconditioningcircuitintoastandardsignalconditioning,tolowerplacemachine;Under16wayswitchquantityafteradoptingthelightintoamac

9、hine.Inthedataprocessingpartoftheneedforcontinuousmonitoringofstateparametersoftheengine,sointheneedforsignalprocessing,storageandtransmission,theuppermachineatthesametime,accordingtotheneedtoreceivethesignalinrealtimeand讦samplesvaluesmorethanitsupperandlowergivealarm,includingbuzzerlowerplacemachin

10、eandsuperordinationmachinescreenalarm;PCthedatadisplaymodeincludingcurvedisplay,digitaldisplay,simulationtabledisplayandrecordthebrowsing;Thedatacommunicationbetweenuppermachineandlowermachinewayusingserialcommunication.Inordertoimprovetheextensibilityandadaptabilityofenginestatemonitoringsystem,the

11、systemdesignedcanworkinthreeways:airborneoperationmode,dataplaybackmodeandgroundtestmode,includingairborneoperationmodecanbePC/104modulesseparatelyintheformoftheairbornelaunchduringtherealflighttest,becauseofthePC/104modules,smallvolume,highreliability,hightemperatureresistanceandresistancetoadverse

12、conditions,welladaptedtotheflightenvironment,tothepartsoftheflightstateandparametersintheflightdetailsandaccurateacquisition,dataprocessingandatthesametime,allthedataarestoredinthesolidplate,inordertoperformdataplaybackandanalysisofengineperformanceinthefuture;Dataplaybackmodecanbekeptinaflighttestd

13、atasenttothePCviaaserialportcommunication,PCreceivesthedatareal-timedisplay,includingusingdigitalwatchdisplaythedataintheformofclear,atthesametimealsotosimulateimage,intheformoftableofdata,andinadditionyoucanalsochoosetousedisplaymodewiththecurvewillbetestingthestateparameterofdynamicdisplay,andfina

14、llytothereceiveddatastoredinharddisk;Groundtestmethodsorganiccombinationoftheairborneplaybackmode,operationmodeanddatawillbecollectedintheprocessofenginetestparametersareprocessed,thenreal-timetransmittingthemviaaserialporttothePC4,PCcandisplaythedatainrealtimeagainatthesametimetosavethem.Inordertoi

15、mprovethereliabilityofthesystem,makethesystemself-checkfunctionandredundantYuJiegou,accordingtothesystemfaultconditionstochangethemodulationcircuitordowntime.Accordingtotherequirementsofaircraftenginetestof20analogquantityandfrequency,andquantityof16wayswitchsamplingfrequencyissetto20ms,analogsignal

16、processingprecisionfor12,andallrecuperatedinto05V.Syntheticallyconsideringthefactors,thesystemsuppermachineandlowermachineUSESthemicrocomputer,andselectsthematurityoftheA/DconversionboardanddigitalI/Oboardtocollectsignals,anddesignedthesignaldisposalcircuitofsignalisolation,filteringandamplification

17、processing,transformationintoAstandardsignal.Softwareusedtodevelopwaystomeetthesystemrequirements.Accordingtotheworkingenvironmenttemperature,humidity,vibrationresistanceandanti-interferencerequirements,choosethePC/104bus,andlowerplacemachineandperipheralboardshavetochoosethePC/104module,inordertome

18、ettheaircraftairborneequipmentrequirementfortheweight,volume,etc.conditionmonitoringsystemhardwaredesignBasedonthesystemoveralldesign,thewholemonitoringsystemhardwareisshowninfigure1USEShardwarestructureclassifiers,byAP4PCandAPC/104intoAunit,underthelowermachineandPC/104motherboard,peripheralinterfa

19、cecard,andallkindsofcircuit,andvariousperipheralinterfacecardcircuitincluding:3PC/104A/Dconversionboard,2piecesofPC/104digitalI/Oboard,light1PC/104multi-functionacquisitionboard,terminalboard,signaldisposalcircuitswitchingcircuitandfield/testing.PC/104motherboards,PC/104A/DconversionboardandPC/104di

20、gitallighteveryI/OboardimplementationofenginesimulationsignalmeasureandfrequencyA/Dconversionandcollection,aswellastotheamountofenginedigitalsignalisolation,andsignaldataprocessingofcollection,storageandtransmission.PC/104multi-functionacquisitionboardsandself-inspection/sceneswitchingcircuitisusedt

21、oimplementthesystemself-checkingandsitedataacquisitionofswitching,andsendingself-checkingvoltage.Signalconditioningcircuittoisolation,filtering,amplifyingthesignal,theytransformintostandardsignal,andthenintoamachine.PCareusedtoimplementthedataacquisitionmachinebysendingdatareceiving,storage,displaya

22、ndalarm.3conditionmonitoringsystemsoftwaredesignOftheconditionmonitoringsystemsoftwaremodulesgoalistodevelopasetofapplicabletotheaircraftengineconditionmonitoringplatformsystem,itcanreal-timehighpressureintheengineworkingprocessspeed,throttleAngle,displacement,oilinjectionnozzlelocation,thefuelflowr

23、ate,vibrationofX,Y,atmospherictemperature,T,5,7Ttemperature,oiltemperature,oiltemperature,hydraulictemperature,carframeunderstaticpressure,thestaticpressure,highpressure,fueloilpressure,oilpressureandhydraulicoilpressure,etc.17analogand3road,frequency,and16wayswitchfordataacquisition,processing,stor

24、age,operation,suchascommunication,statusdisplayandalarmsoftwarerunningontheuppermachineandlowermachinerespectively,systemspecificfeaturesinclude:1stateparameterreal-timecollectionandprocessingInthesystem,completeenginevariousreal-timeacquisitionofstateparameter,andtheassociatedwiththestateparametero

25、fprocessingandcalculation,andthedeviationsfromthenormalrangeofstateparametersonthetag,toanalyzetheengineworkingcondition.3.2real-timestatusparametersandplaybackdatatransmissionOnthesurfaceofthetestmodeandonlinedataplaybackmode,amachineunderthePC/104collectedstatusparametersviaaserialportinreal-timet

26、ransmissiontothePC,andsavetothedatabaseonaPC.3.3statusmonitoringandreal-timedatacontrolsandrelatedtouseofdrawingtoolstosimulatetheacquisitionstateparametersofthedigitaldisplayandthetableshows,anddrawthetimecurvesothattheobservationparameteroftheparametersofthedynamicchangeandtrendofthefuture,whichca

27、nmonitortheworkingstateoftheengineatdifferenttimes,toachievethepurposeofconditionmonitoring.3.4alarmoutputandprintWhenthecollectiontothestateoftheparametervaluesdeviatefromnormalrangeafter,throughthevoicewarningcolortooperatingpersonnel,location,anddisplayalarminginformation,andallthewarningpointdat

28、acanbeextractedfordisplay,analysisandprinting.4self-checkingsystemandredundancydesign4.1self-checkingsystemsignaldisposalsystemisanimportantpartofgeneraldataacquisitionsystem,regulatewontcreateanyproblemsfordigitalsignal,however,onthechoiceofdesignandphysicalcomponentsisdifficulttoguaranteetheanalog

29、channelsignalinputandoutputequalstheabsolute,foranalogsignaldataacquisitionsystemofthemainsourceoferroristhesystemerror,sothedatamustbetakenintoaccounttheerroranderrorcorrectiontoimprovetheaccuracyofthedata,apparently,errorcorrectionismainlyinviewoftheanalogchannelisconcerned.Signalconditioningparti

30、nuseafterperiodoftimethereisadeviation,errorcharacteristicsoftheanalogchannelmayovertimeslowlychanging,digitalchannelandanalogchannelinthesystemismore,thenumberofregularmanualmeasurementoftheintegrityofeachchannelandchannelcharacteristicsisimpossible,soaself-checkingsystemisdesignedtomeetthisrequire

31、ment,thesystemofself-inspectionsystemconsistsoftwofunctions:testingthecorrectnessoftheregulatechannel;Calculationerrorcharacteristicsoftheanalogchannel.Theself-checkingsystemregularlyornotregularlybythesystemautomaticallyorartificialtriggerswitchschematicdiagram.Theimplementationoftheself-checkingpr

32、ocessisasfollows:UnderthePC/104aself-inspectionprograminthemachinethroughthePC/104multi-functionacquisitionboardstoKporttheself-checkvoltageof5V,thesystementerstheself-checkstate.throughthePC/104multi-functionacquisitionboardssentTAandTDportsrespectivelysimulatedself-checkingvoltageandvoltagedigital

33、testing.throughthePC/104A/DconversionboardandPC/104digitalI/Oboardisintrospectedthesignalacquisition.theself-inspectionprogramtoanalyzeself-checkingsignaldataprocessing.Duetotheconditionmonitoringsystemsenvironmentisverybad,andtherunningtimeoftheengineconditionmonitoringsystemisgenerallyisverylong,s

34、othesignaldisposalcircuitselectshighreliabilityofthecomponentsasfaraspossible,atthesametimeinordertopreventfailureintheoperationofthesystempartcausedbyfailure,youshouldalsouseredundantcircuitstoimprovesystemreliabilityandaccuracy,andinsomecases,monitoringsystemforeachsignalallthewaytoincreaseasamefu

35、nctionofredundancycontrolcircuit,inordertoincreaseitsreliability.Becauseofthemonitoringsystemaspartoftheairborneequipment,thereforeshouldbeonthebasisofconsideringtheequipmentvolumeupandimprovethereliabilityofsystem,thesystemmonitoringdataaccordingtothecircuitcharacteristicstoconsiderredundancycontro

36、lcircuitdesign.InthesystemofthecommunistpartyofChina17frequencyanalogand3road,whichisdividedinto6groups,signalsaregroupedasshownintable1,including17roadanalogwasdividedinto5groups,3roadfrequencyquantityis1setalone,eachgroupusethesamesignaldisposalcircuitundertakerecuperating,therefore,theredundancyo

37、fthesystemcircuitdesign,makefulluseoftheconditionsineachgroupsharearedundantsignalregulatecircuit,namelyeachgroupusethesamemodulationcircuit,respectively,usingtheoriginalcontrolsignalinnormaloperationofcircuit,whenthesetisinanywaythesignalconditioningcircuitfailureoccurs,canswitchtothestandbyredunda

38、ncycontrolcircuit,continuingstatemonitoring,soastoimprovetheaccuracyandreliabilityofsystem,duetothesignalineachgroupshareaconditioningcircuit,andwillinitiallyneedtoincreaseredundant20roadsonsignaldisposalcircuitmodulecircuit,reducedtosimplyaddno.6redundancysubcircuitforsignaldisposalcircuit,greatlyr

39、educingtheregulatethenumberofsubcircuit,andimprovetheaccuracyandreliabilityofthesystem.Accordingtotheaboveanalysisofthemonitoringsystemformonitoringsignalandmodulationcircuit,designofthenursingchildson/redundantcircuitswitchingcircuit,theeventofafailureregulatecircuitandredundantcircuitswitchingproc

40、essisasfollows：2-sinx/、y=+u(t)(14)2+smxW(t)istheoutputofthehysteresissystem.Assumingthatw(t)isequaltozero,thenthesystemisnotstable,becauseforanyx.y=2-sinx+u(t)O.Duringthesimulation,usingthegeneralized2+sinxRBFneuralnetworkformodelingofinversehysteresismodel.Inputcontrolsignalforr=6.5sin2.3tandtheout

41、putoftheneuralnetworkinversemodelforv(t),asshowninfigure3,themodelbytheneuralnetworkinversehysteresissystemundertheactionofsingleoutputfor1w(t),asshowninfigure4.Ascanbeseenfromthefigure3andfigure4,greatlyweakened,hysteresisandhysteresisphenomenonbasicallyeliminated.ParametersofPIDcontrolleris:p=70K,

42、K=0.005Kd=O.Bang-Bangcontrolruleis:A=1.5,KB=50,SpandSp12are0.03and0.02respectively.Thefigure5isnotplusBang-Bangcontrolsimulationresults,namelyfortheNPIDcontrol,figure6,7,&andBang-BangcontrolafterNBPIDcontrolsimulationresults.4conclusionHasgoodcharacteristicsthroughtheuseofgeneralizedRBFneuralnetwork

43、,directinversemodelofhysteresissystemmodeling,andthenusetheinversemodeloftheimplementationoffeedforwardcontrol,cangreatlyreducethehysteresisphenomenon.ByjoiningBang-Bangcontrol,caneffectivelycontrolerror.Ascanbeseenfromthesimulationresults,basedonfeedforwardcontrolplusBang-BangcontrolofPIDcontrol,th

44、ehysteresissystemcanbeeffectivelycontrolled.Thismethodcanalsobeextendedtoothertypesofhysteresiscontrolsystem.References:1HamdanM,GaoZQ.AnovelPIDcontrollerforpneumaticproportionalvalveswithhysteresisJ.IEEE,2000,2:1198-1201.2ZhaoHongwei,etc.Piezoelectricceramicactuatorintheapplicationofflexiblemanipul

45、atorrobotresearchJ.Journalofpiezoelectricandacoustics,2000,22(3):173-176.3ChoiGS,KimHS,ChoiGH.AstudyonpositioncontrolofpiezoelectricacuatorsA.ISIE97C.Portugal,1997.4TaoG,KokotovicPV.AdaptivecontrolofplantswithunknownhysteresisJ.IEEETrans.Autom.Contr.1995,40(2):200-212.5SUCY,StepanenkoY,SvobodaJ,etal

46、.RobustadaptivecontrolofaclassofnonlinearsystemsJ.IEEETran.Au.to.Con.2000,45(12):2427-2432.6Cruz-HernndezJM,HaywardV.PhasecontrolapproachtohysteresisreductionJ.IEEETran.onContr.Sys.Tech.2001,9(1):17-26.7HwangCL,JanC,ChenYH.PiezomechanicsusingintelliAgentvariable-structurecontrolJ.IEEETran.onIndustri

47、alElectonics.2001,48(1):47-59.8HanJM.T.A.Adriaens.WillemL.deKoning,ReinderBanning.ModelingpiezoelectricactuatorsJ.IEEE/ASMETran.Mech.2000,5(4):331-341.9wangyongjistuff.NeuralnetworkcontrolM.Machineryindustrypress,10HaykinS.NeuralNetworksM.Prentice-HallInc.1999.航空发动机状态监测系统设计研究康文雄、李华聪、杨勇柯(1.华南理工大学,广东广

48、州510640;2.西北工业大学,陕西西安710072)摘要:以某型航空发动机为研究对象,讨论了发动机状态监测系统的设计和实现,主要探讨了状态监测系统的总体设计,软硬件开发及自检系统和冗余设计,并在发动机状态监测系统的设计中引入了嵌入式PC/104模块。为了使状态监测系统具有更好的扩展性和适应性,将系统设计成可以在三种方式下工作:机载运行方式、数据回放方式和地面试车方式,通过这些方式对发动机状态参数进行自动监测,为发动机的状态趋势分析、故障诊断和视情维修提供科学的依据。关键词:发动机状态监测;PC/104;冗余设计0.引言作为飞机飞行的动力源,航空发动机的研制是一个非常复杂的过程,而试验作为研

49、制航空发动机的三大支柱(计算、制造和试验)之一,其重要性不言而喻,事实证明,发动机主要是靠试验出来的,而不是靠计算分析出来的。对于一个航空发动机的研制群体来说,具有怎平,就决定着能够研制出怎样水平的发动机。对于航空发动机的试制而言,状态监测是发动机性能的重要检测手段,通过状态监测和试车工作是发动机达到调整性能、磨合运转、检查制造或大修质量,最终给出发动机出厂性能报告的目的,因此采用精确可靠的测试手段来进行状态监测对于保证发动机质量具有重要的意义。众所周知,发动机工作过程中的振动大、噪声高以及其强烈的干扰信号,都对多种参数的监测系统提出了更高的要求。特别是随着发动机性能的提高,状态监测时所需要实

50、时监测的参数越来越多,多年来人们不断探索新的测试技术,以适应日益发展着的发动机试验技术的要求。.状态监测系统总体设计该状态监测系统是针对某型涡扇发动机设计的,在此发动机监测系统中的输入信号部分共有17路模拟量、3路频率量以及16路开关量,其中17路模拟量、3路频率量通过信号调理电路调理成标准信号,送入下位机中;16路开关量采用光隔离后送入下位机中。在数据处理部分中需要对发动机的状态参数进行连续的监测,因此在采用的同时需要对信号进行处理、保存和传输,同时上位机需要对信号进行实时接收并显示,如果采样值超过其上下限则给与报警,包括下位机的蜂鸣和上位机的屏幕报警;上位机中的数据显示方式包括曲线显示,数

51、字显示,模拟表显示和记录浏览方式显示;上位机和下位机之间的数据通信方式采用串行通信来进行。为了提高发动机状态监测系统的扩展性和适应性,将系统设计成可以在三种方式下工作:机载运行方式、数据回放方式和地面试车方式,其中机载运行方式可以将PC/104模块以机载的方式单独搭载在真正的飞行试验中,由于PC/104模块的小体积、高可靠性、抗高温和抗恶劣条件等优点,很好的适应了飞行环境,可以对飞行中各部件状态和飞行中各项参数进行详细记录和准确采集,并同时进行数据处理,所有的数据都保存在固态盘中,以便于日后进行数据回放和对发动机进行性能分析;数据回放方式可以将在飞行试验中保存的数据通过串口通信传送到上位机,上

52、位机将接收到的数据实时的显示出来,其中利用数字表的形式将数据清楚显示出来,同时还以模拟表的形式形象的表示出数据的变化,除此之外还可以选择使用以曲线显示方式将被检测的状态参数动态的显示出来,最后将所接收的数据保存在硬盘中;地面试车方式有机的结合了机载运行方式和数据回放方式,将发动机试车过程中采集到的参量经过处理,再通过串口将它们实时的传送到上位机4,上位机再将数据实时的显示出来,同时将它们进行保存。为提高系统的可靠性,使系统带有自检功能和冗余结构,根据系统的故障情况给与更换调理电路或停机。根据航空发动机测试的要求,对20路模拟量和频率量,及16路开关量的采样频率设为20ms,模拟量信号处理精度为

53、12位,并全部调理成05V。综合考虑各方面因素,系统的上位机和下位机都采用微机,同时选用成熟的A/D转换板和数字I/O板来采集信号,并自行设计信号调理电路对信号进行隔离、滤波、放大等处理,变换成标准信号。软件采用自行开发方式来满足系统需求。根据系统的工作环境对温度、湿度、抗震性和抗干扰性的要求,选用PC/104总线,同时下位机及外围板卡都选用了PC/104模块,以满足航空机载设备对重量、体积等方面的要求。状态监测系统硬件设计根据系统总体设计方案,整个监测系统硬件采用了图1硬件组成结构图分级机构,由一台P4的上位机和一台PC/104下位机组成,下位机又分为PC/104主机板、外围板卡及各种电路,

54、其中外围板卡和各种电路包括:3块PC/104AD转换板,2块PC/104数字光隔1/O板,1块PC/104多功能采集板,接线端子板,信号调理电路及现场/自检切换电路PC/104主机板、PC/104AD转换板及PC/104数字光隔I/O板实现对发动机模拟信号量和频率量的A/D转换和采集,以及对发动机数字信号量的隔离采集,并对采集的信号进行数据处理,存储和传输。PC/104多功能采集板及自检/现场切换电路用来实现对系统自检和现场数据采集的切换,以及自检电压的发送。信号调理电路对信号进行隔离、滤波、放大等处理,将它们都变换成标准信号,然后送入下位机。上位机用于实现对数据采集机所发送数据的接收、存储、

55、显示和报警。、状态监测系统软件设计该状态监测系统软件模块的目标是开发一套适用于航空发动机状态监测的平台系统,它可以实时的对发动机工作过程中高压转速、油门角度、喷口位移、油针位置、燃油流量、振动X、振动Y、大气温度、T5温度、T7温度、燃油温度、滑油温度、液压温度、车台静压、外函静压、高压出压、燃油进油压力、滑油压力、液压油压力等17路模拟量和3路频率量,以及16路开关量进行数据采集、处理、存储、通信、状态显示和报警等操作,软件分别运行在上位机和下位机上,系统具体功能包括:3、1实时状态参数的采集和处理在该系统中,完成发动机各种状态参数的实时采集,并对采集的状态参数进行相关的处理和运算,并对偏离

56、正常值一定的范围的状态参数作上标记,以便事后对发动机工作状况进行分析。3、2实时状态参数和回放数据的传输在地面试车方式和联机数据回放方式时,对PC/104下位机采集到的状态参数通过串口实时的传输到上位机,并保存到上位机的数据库中。3、3状态的监测和实时数据的显示利用相关的控件和绘图工具对采集的状态参数进行数字显示和模拟表显示,并绘制出参数的时间曲线以便于观测参数的动态变化及未来趋势,从而能够监视发动机在不同时刻的工作状态,达到状态监测的目的。3、4报警输出和打印当采集到的状态参数值偏离正常值一定的范围后,通过声音、位置和警示色来向操作人员显示报警信息,并可以将所有的警告点数据提取出来进行显示、

57、分析和打印。自检系统及冗余设计4、1自检系统信号调理系统是一般数据采集系统的重要组成部分,对于数字信号的调理不会产生任何问题,然而在设计和物理器件的选择上难以保证模拟通道信号输入与输出的绝对相等,对于模拟信号来说信号调理系统的误差将是整个系统误差的主要来源,所以采集的数据必须考虑这个误差并进行误差校正以提高数据的准确性,显然,误差校正主要是针对模拟通道而言的。信号调理部分在使用一段时间后存在着偏差,模拟通道的误差特性也可能随着时间而缓慢变化,在该系统中数字通道和模拟通道的数量较多,定期手工测量每个通道的完好性和通道特性是不可能的,所以设计一套自检系统来满足这个要求,该系统的自检系统包括两个功能:检测调理通道的正确性;计算模拟通道的误差特性。该自检系统定期或不定期的由系统自动进行或人工触发进行。自检过程的实现过程如下:(1)PC/104下位机中的自检程序通过PC/104多功能采集板向端口K发出5V的自检电压,此时系统进入自检状态。通过PC/104多功能采集板分别向TA和TD端口发出模拟自检电压和数字自检电压。(3)通过PC/104A/D转换板和PC/104数字I/O板进行自检信号的采集。(4)自检程序对自检信号数据进行分析处理。4、2冗余设计由于该状态监测系统所处的环境极为恶劣,以及发动机状态监